EP2843244B1 - Suppression de séparation de flux d'air provoquée par des chocs - Google Patents
Suppression de séparation de flux d'air provoquée par des chocs Download PDFInfo
- Publication number
- EP2843244B1 EP2843244B1 EP14178046.0A EP14178046A EP2843244B1 EP 2843244 B1 EP2843244 B1 EP 2843244B1 EP 14178046 A EP14178046 A EP 14178046A EP 2843244 B1 EP2843244 B1 EP 2843244B1
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- EP
- European Patent Office
- Prior art keywords
- fluid
- actuators
- boundary layer
- actuator
- wall
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Links
- 238000000926 separation method Methods 0.000 title claims description 29
- 230000035939 shock Effects 0.000 title claims description 17
- 230000001629 suppression Effects 0.000 title description 5
- 239000012530 fluid Substances 0.000 claims description 67
- 238000000034 method Methods 0.000 claims description 12
- 238000003491 array Methods 0.000 claims description 11
- 230000006835 compression Effects 0.000 claims description 8
- 238000007906 compression Methods 0.000 claims description 8
- 230000000644 propagated effect Effects 0.000 claims description 3
- 238000011144 upstream manufacturing Methods 0.000 description 4
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000003467 diminishing effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
- F15D1/00—Influencing flow of fluids
- F15D1/0095—Influencing flow of fluids by means of injecting jet pulses of fluid wherein the injected fluid is taken from the fluid and re-injected again, e.g. synthetic jet actuators
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
- B64C21/025—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for simultaneous blowing and sucking
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0226—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising boundary layer control means
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0253—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft
- B64D2033/026—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft for supersonic or hypersonic aircraft
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T137/00—Fluid handling
- Y10T137/0318—Processes
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T137/00—Fluid handling
- Y10T137/0536—Highspeed fluid intake means [e.g., jet engine intake]
Definitions
- This application relates generally to the suppression of shock-induced separation of high speed jet inlet airflow from a relatively low-energy boundary layer.
- the actuators are positioned to direct exhaled fluid back into the boundary layer in a generally downstream exhalation direction.
- the actuators are zero-net-mass-flux (ZNMF) actuators.
- ZNMF zero-net-mass-flux
- each actuator of the array is configured to alternately inhale and exhale fluid in an operation cycle of each actuator, and the operation cycles of the actuators are phased with one another such that the cycle of each actuator of an array leads ahead of at least one other actuator of the array and lags behind at least one other actuator of the array.
- each actuator may be slowed during an inhalation portion of its operation cycle relative to an exhalation portion such that more time is spent drawing fluid than directing it downstream.
- the wall is a generally continuous interior wall of an axisymmetric mixed compression inlet.
- the wall is a generally continuous interior wall of a non-axisymmetric mixed compression inlet.
- the actuators of the phased actuator array are positioned and oriented to inhale and exhale boundary layer fluid through a downstream-facing step in the wall.
- the actuators of the phased actuator array are positioned and oriented to inhale and exhale boundary layer fluid through a recessed wall port.
- the method includes the additional step of directing fluid back into the boundary layer in a generally downstream exhalation direction.
- the method optionally includes the additional step of alternating the drawing and directing steps.
- the step of drawing fluid from a boundary layer separation bubble includes causing ZNMF actuators to inhale fluid from the boundary layer separation bubble during an inhalation portion of an operation cycle of the ZNMF actuators.
- the step of directing fluid back into the boundary layer includes causing ZNMF actuators to direct fluid back into the boundary layer in a generally downstream exhalation direction during an exhalation portion of the operation cycle of the ZNMF actuators.
- the alternating step includes causing ZNMF actuators to alternately inhale fluid from and exhale fluid into the boundary layer.
- the drawing, directing, and alternating steps include causing each of at least two ZNMF actuators to alternately inhale fluid from and exhale fluid into the boundary layer during respective operation cycles of the actuators, the operation cycles of the actuators being phased with one another such that the cycle of each actuator leads ahead of at least one other actuator of the array and lags behind at least one other actuator of the array.
- the step of alternating the drawing and directing steps includes the additional step of slowing or speeding the actuators during one of the drawing step and the directing step such that one of the drawing step and the directing step takes more time to complete than the other.
- the step of alternating the drawing and directing steps includes slowing the drawing step or speeding the directing step such that the drawing step takes more time to complete than the directing step.
- FIG. 1-5 An apparatus for suppressing shock-induced separation of high speed jet inlet airflow from a relatively low-energy boundary layer is generally shown at 10 in Figures 1-5 , 9, and 10 .
- a second embodiment is generally shown at 10' in Figures 6-8 .
- Reference numerals with the designation prime (') in Figures 6-8 indicate alternative configurations of elements that also appear in the first embodiment. Unless indicated otherwise, where a portion of the following description uses a reference numeral to refer to Figures 1-5 , 9, and 10 , that portion of the description applies equally to elements designated by primed numerals in Figures 6-8 .
- the apparatus 10 includes a plurality of actuators 14 mounted to a wall 12.
- Each actuator 14 is configured to alternately inhale and exhale fluid, such as air, at a rapid rate in an operation cycle.
- the actuators 14 may be zero-net-mass-flux (ZNMF) actuators, but in other embodiments may be any other suitable type of actuator.
- ZNMF zero-net-mass-flux
- each actuator 14 may be located in a position along the wall where it can alternately inhale fluid from and exhale fluid into a relatively low-energy boundary layer of a fluid mass 16 flowing along the wall 12.
- Each actuator 14 may further be positioned such that an inhalation portion of its operation cycle may cause it to inhale low energy fluid from a flow separation region or boundary layer separation bubble 18 induced by a supersonic shock wave 20 propagated in the fluid mass 16.
- Each actuator 14 may also be positioned such that it will inhale fluid from a position downstream from an upstream end of the separation bubble 18 and upstream from a downstream end of the bubble 18.
- the actuators 14 of the apparatus 10 are positioned to energize a boundary layer by directing exhaled fluid back into the boundary layer in a generally downstream exhalation direction. So configured and positioned, the actuators 14 of the apparatus 10 are able to diminish or at least partially collapse the separation bubble 18 while energizing the boundary layer, thus preventing blockage, pressure losses, and possible unstart of an engine inlet.
- the apparatus 10 includes phased actuator arrays 22 that each comprise at least two actuators 14 (four shown in Figure 2 ).
- the actuators 14 are disposed adjacent one another and arranged along the wall 12 transverse to a flow direction 21 of the fluid mass 16.
- Each actuator 14 of each array 22 may be configured to alternately inhale and exhale fluid at a rapid rate in an operation cycle, and each actuator 14 may be positioned to alternately inhale and exhale fluid from and into a boundary layer of a fluid mass 16 flowing along the wall 12.
- the operation cycles of the actuators 14 in a four-actuator array 22 may be phased with one another such that the cycle for each actuator 14 begins after the other three actuators in the array have completed 90, 180 and 270 degrees (i.e., one quarter, one half and three quarters) of their cycles. This phasing assures that "inhaling" is always occurring somewhere within each array 22, and overall fluctuations associated with the operation are smoothed.
- the drawing, directing, and alternating steps may include causing each of at least two ZNMF actuators to alternately inhale fluid from and exhale fluid into the boundary layer during respective operation cycles of the actuators 14.
- the operation cycles of the actuators 14 may be phased with one another such that the cycle of each actuator leads ahead or lags behind those of neighboring actuators in a precise manner to optimize performance and reduce overall vibration.
- the duty cycle of each individual actuator 14 may also be modified to increase the portion of each cycle dedicated to the "inhale" (i.e., to inhale slowly and exhale quickly). This operating cycle configuration may further enhance the constancy of separation bubble diminution in the vicinity of the array 22.
- a plurality of phased actuator arrays 22 is disposed adjacent one another and distributed along the wall 12 transverse to the flow direction of the fluid mass 16.
- the actuator arrays 22 are disposed in respective locations where a boundary layer separation bubble 18 forms along the wall 12 when the fluid mass 16 is flowing, such that the arrays 22 are able to diminish a larger portion of a separation bubble 18 that forms along the wall 12 transverse to the flow direction.
- the wall 12 is a continuous interior wall of an engine inlet 24.
- the wall 12 may be either an inner circumferential inlet wall 23 or an outer circumferential compression spike wall 25.
- the plurality of phased actuator arrays 22 may be distributed in a continuous linear array around the continuous interior wall 12 of the engine inlet 24 to provide uniform diminishment of a separation bubble 18 that forms around the continuous interior wall 12.
- This distribution of arrays 22 may be applied with similar effectiveness whether the wall 12 is a continuous interior wall 23 of an axisymmetric mixed compression inlet 26 as shown in Figure 1 , an exterior surface 25 of a compression spike 28 in the axisymmetric inlet 26, or an interior surface of a non-axisymmetric (e.g., "2-D") mixed compression inlet 30 as shown in Figures 9 and 10 .
- a non-axisymmetric (e.g., "2-D") mixed compression inlet 30 as shown in Figures 9 and 10 .
- the wall 12 may include a downstream-facing step 32, and the actuators 14 of the phased actuator array 22 may be positioned and oriented to inhale and exhale boundary layer fluid through the downstream-facing step 32.
- each actuator 14' of the phased actuator array 22' may be positioned and oriented to inhale and exhale boundary layer fluid through a recessed wall port 34.
- shock-induced separation of high speed jet inlet airflow from a relatively low-energy boundary layer may be suppressed by drawing low energy fluid from the boundary layer separation bubble 18 induced along a wall 12. This may be done by commencing an inhalation portion of an operation cycle of the ZNMF actuators 14 as shown in Figure 4 .
- the inhalation portion of the cycle may include causing the ZNMF actuators 14 to inhale fluid from a position downstream from the upstream end of the separation bubble 18 and upstream from the downstream end of the bubble 18.
- the actuators 14 may inhale fluid from an interior portion of the bubble 18.
- the exhalation portion of the cycle may comprise causing the ZNMF actuators 14 to alternately inhale fluid from and exhale fluid into the boundary layer at a rapid rate.
- the operational frequency of a ZNMF actuator is typically governed by its material properties, shape and size, which are driven by the environment and available volume for housing the installed actuator(s).
- a representative actuator for the wind turbine application would have a diameter, thickness, operational frequency and duty cycle (fraction of time spent exhaling) of approximately 3 inches, 1 ⁇ 4 inch, 800 Hz and 50%, respectively.
- the maximum speed of the exhaled air may be several hundred feet per second (over half of the local speed of sound). However, actuators with different properties may be employed and operated at the conditions best suited for optimum performance.
- the operation cycles of the actuators 14 may be phased with one another according to the number of actuators per array (e.g., 90 degrees of phasing for an array with 4 actuators).
- the operation cycles may be asymmetric, i.e., each actuator 14 may be slowed during its inhalation portion of the operation cycle, relative to the exhalation portion, such that more time is spent drawing fluid than directing it downstream.
- each actuator 14 may be configured such that directing the fluid may require more time to complete than drawing the fluid.
- each actuator 14 may also be configured to alternate between operation cycles that prolong the drawing or directing of fluid.
- An airflow separation suppression apparatus constructed and implemented as described above may prevent blockage, pressure losses, and possible unstart of an engine inlet, by diminishing, energizing, at least partially collapsing, and/or suppressing formation of a boundary layer separation bubble induced by a supersonic shock wave propagated in a fluid mass in a high speed jet inlet.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Analytical Chemistry (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Jet Pumps And Other Pumps (AREA)
- Wind Motors (AREA)
Claims (15)
- Appareil (10) pour supprimer la séparation induite par un choc d'un écoulement d'air à grande vitesse à partir d'une couche limite d'énergie relativement faible d'une masse fluide s'écoulant le long d'une paroi, l'appareil comprenant :une entrée de moteur (24) comprenant une paroi intérieure généralement continue (12) ; etune pluralité d'actionneurs (14) configurés pour inhaler alternativement le fluide d'une bulle de séparation de couche limite induite par un choc et pour expirer le fluide ;dans lequel l'appareil comprend une pluralité de réseaux d'actionneurs en phase (22) comprenant chacun une pluralité desdits actionneurs (14) disposés les uns à côté des autres et répartis le long de la paroi intérieure (12) transversalement à la direction d'écoulement de la masse fluide, dans des emplacements respectifs où la bulle de séparation de la couche limite se forme le long de la paroi intérieure (12) lorsque la masse fluide s'écoule ;la pluralité de réseaux d'actionneurs en phase sont répartis autour de la paroi intérieure généralement continue de l'entrée de moteur ; etles actionneurs sont positionnés pour rediriger le fluide expiré dans la couche limite dans une direction d'expiration généralement en aval.
- Appareil (10) selon la revendication 1, dans lequel les actionneurs sont des actionneurs à flux massique net nul (ZNMF).
- Appareil (10) selon la revendication 1 ou 2, dans lequel chaque actionneur (14) du réseau (22) est configuré pour inhaler et expirer alternativement du fluide dans un cycle de fonctionnement de chaque actionneur (14), les cycles de fonctionnement des actionneurs étant mis en phase les uns avec les autres de sorte que le cycle de chaque actionneur (14) précède au moins un autre actionneur (14) du réseau et soit en retard par rapport à au moins un autre actionneur (14) du réseau (22).
- Appareil (10) selon l'une quelconque des revendications 1 à 3, dans lequel chaque actionneur (14) peut être ralenti pendant une partie d'inhalation de son cycle de fonctionnement par rapport à une partie d'expiration de telle sorte que plus de temps est passé à aspirer le fluide qu'à le diriger en aval.
- Appareil selon l'une quelconque des revendications précédentes, dans lequel la paroi intérieure (12) est une paroi intérieure généralement continue d'une entrée de compression mixte axisymétrique.
- Appareil selon l'une quelconque des revendications 1 à 4, dans lequel la paroi intérieure (12) est une paroi intérieure généralement continue d'une entrée de compression mixte non axisymétrique.
- Appareil selon l'une quelconque des revendications précédentes, dans lequel chaque actionneur est positionné et orienté pour inhaler et expirer le fluide de la couche limite à travers une marche orientée vers l'aval dans la paroi et / ou dans lequel chaque actionneur est positionné et orienté pour inhaler et expirer le fluide de la couche limite à travers un orifice mural encastré.
- Procédé pour supprimer la séparation induite par un choc du flux d'air d'entrée d'un moteur à grande vitesse d'une couche limite d'énergie relativement faible en :aspirant du fluide à partir d'une bulle de séparation de couche limite induite le long d'une paroi par une onde de choc supersonique propagée dans une masse fluide s'écoulant le long de la paroi en utilisant une pluralité de réseaux d'actionneurs en phase (22) comprenant chacun une pluralité d'actionneurs (14) disposés les uns à côté des autres et répartis le long de la paroi transversalement à la direction d'écoulement de la masse fluide, aux emplacements respectifs où se forme la bulle de séparation de la couche limite le long de la paroi lorsque la masse fluide s'écoule ; eten redirigeant le fluide dans la couche limite dans une direction d'expiration généralement en aval.dans lequel la paroi est une paroi intérieure généralement continue (12) d'une entrée de moteur (24) et la pluralité de réseaux d'actionneurs en phase sont répartis autour de la paroi intérieure généralement continue de l'entrée de moteur.
- Procédé selon la revendication 8, comprenant l'étape supplémentaire d'alternance des étapes d'aspiration et de direction.
- Procédé selon la revendication 9, dans lequel l'étape d'alternance comprend le fait d'amener les actionneurs ZNMF à inhaler et à expirer en alternance du fluide à partir de et vers la couche limite.
- Procédé selon la revendication 8, 9 ou 10, dans lequel l'étape d'aspiration de fluide à partir d'une bulle de séparation de couche limite comprend le fait d'amener les actionneurs ZNMF à inhaler le fluide à partir de la bulle de séparation de couche limite pendant une partie d'inhalation d'un cycle de fonctionnement des actionneurs ZNMF.
- Procédé selon la revendication 10 ou 11, dans lequel l'étape de redirection de fluide dans la couche limite comprend le fait d'amener les actionneurs ZNMF à rediriger le fluide dans la couche limite dans une direction d'expiration généralement en aval pendant une partie d'expiration du cycle de fonctionnement des actionneurs ZNMF
- Procédé selon l'une quelconque des revendications 9 à 12, dans lequel les étapes d'aspiration, de direction et d'alternance consistent à amener chacun d'au moins deux actionneurs ZNMEF à inhaler et à expirer alternativement le fluide de la couche limite pendant les cycles de fonctionnement respectifs des actionneurs, les cycles de fonctionnement des actionneurs étant mis en phase les uns avec les autres de sorte que le cycle de chaque actionneur précède au moins un autre actionneur du réseau et soit en retard par rapport à au moins un autre actionneur du réseau.
- Procédé selon l'une quelconque des revendications 9 à 13, dans lequel l'étape d'alternance des étapes d'aspiration et de direction comprend l'étape supplémentaire de ralentissement ou d'accélération des actionneurs pendant l'une des étapes d'aspiration et de direction telle que l'une des étapes d'aspiration et de direction prend plus de temps à se terminer que l'autre.
- Procédé selon la revendication 14, dans lequel l'étape d'alternance des étapes d'aspiration et de direction comprend le ralentissement de l'étape d'aspiration ou l'accélération de l'étape de direction de telle sorte que l'étape d'aspiration prend plus de temps à se terminer que l'étape de direction.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/952,088 US10054048B2 (en) | 2013-07-26 | 2013-07-26 | Suprression of shock-induced airflow separation |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2843244A2 EP2843244A2 (fr) | 2015-03-04 |
EP2843244A3 EP2843244A3 (fr) | 2015-07-29 |
EP2843244B1 true EP2843244B1 (fr) | 2020-11-25 |
Family
ID=51220440
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP14178046.0A Active EP2843244B1 (fr) | 2013-07-26 | 2014-07-22 | Suppression de séparation de flux d'air provoquée par des chocs |
Country Status (3)
Country | Link |
---|---|
US (1) | US10054048B2 (fr) |
EP (1) | EP2843244B1 (fr) |
JP (1) | JP6422253B2 (fr) |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10502246B2 (en) | 2016-04-25 | 2019-12-10 | Rensselaer Polytechnic Institute | Methods and apparatus for controlling flow fields |
US11542866B2 (en) * | 2020-05-13 | 2023-01-03 | The Boeing Company | Adaptable flow control for engine nacelles |
CN112572810A (zh) * | 2020-11-25 | 2021-03-30 | 北京空天技术研究所 | 一种进气道边界层分离消除装置及飞行器 |
CN115559814B (zh) * | 2022-10-31 | 2023-06-20 | 南京航空航天大学 | 一种边界层吸入式进气道及内流控制装置 |
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JP2015042900A (ja) | 2015-03-05 |
US10054048B2 (en) | 2018-08-21 |
EP2843244A3 (fr) | 2015-07-29 |
US20150027545A1 (en) | 2015-01-29 |
JP6422253B2 (ja) | 2018-11-14 |
EP2843244A2 (fr) | 2015-03-04 |
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